• 한국항공우주학회지
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• 제50권7호
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• pp.445-454
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• 2022

항공기가 빙점 이하의 습도가 높은 구름대를 지날 때 액적이 항공기와 충돌하면 날개, 동체 등 항공기 구성품에 결빙이 발생한다. 특히 항공기의 날개에 결빙이 증식되면 공력 성능의 저하와 비행 안정성의 감소 등의 치명적인 안전 문제를 초래할 수 있다. 본 연구에서는 항공기 날개에 적용되는 고양력 장치인 다중 익형의 결빙 증식량이 최소가 되도록 형상 최적설계를 수행하였다. 3차원 Reynolds-Averaged Navier-Stokes 지배 방정식을 이용하여 공력해석을 수행하였고, 다물리 전산해석을 통해 결빙의 형상 및 증식량을 예측하였다. 최적설계의 목적함수는 결빙 증식량 최소화로 설정하였고, 설계변수는 Slat과 Flap의 전개 각도와 위치를 정의하는 형상 변수 6개를 선정하였다. 설계 과정에서 목적함수의 평가는 크리깅 근사모델을 사용하여 대체하였고 유전자 알고리즘을 적용하여 최적 형상을 도출하였다. 최적화를 수행한 결과, Slat과 Flap에 최적의 전개 각도와 위치를 적용하였을 때 결빙 증식량이 약 8% 감소하였다.

• 한국항공우주학회지
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• 제44권11호
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• pp.933-940
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• 2016

본 연구에서는 MW 용량의 풍력터빈 블레이드용 에어포일의 설계 단계에서 성능 검증기법에 대한 비교 연구를 수행하였다. 이를 위해 5~10 MW 해상풍력터빈용으로 설계된 21%와 30% 두께비의 에어포일을 사용하여 풍동시험을 수행하였으며, 레이놀즈 수 $1.0{\times}10^7$ 조건에서의 XFOIL의 해석결과와 상호 비교하였다. 풍동시험은 자유흐름 속도 50 m/s, 시위 기준 레이놀즈 수는 $2.2{\times}10^6$에서 수행되었으며, 표면거칠기 효과는 지그재그 테이프를 사용하여 모사하였다. 비교 결과 풍동시험과 XFOIL 해석에는 차이를 보이지만, 풍동시험을 통해 받음각 변화에 따른 에어포일 표면에서의 압력분포 변화와 기본적인 공력 성능 및 표면거칠기 효과를 확인 할 수 있었다. XFOIL은 설계조건에서 기본적인 양항비와 표면거칠기 효과에 의한 양항비 변화 등을 확인 할 수 있었다.

• 한국항공우주학회지
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• 제30권5호
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• pp.1-8
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• 2002

초소형 비행체(MAV) 프로펠러에서 깃 익형의 공기역학적 특성은 매우 중요한 사항이다. 이를 위해서 저레이놀즈수 익형의 성능예측에 층류에서 난류로의 천이과정을 포함하는 XFOIL을 이용하여 프로펠러 깃 익형 단면의 양력과 항력 분포를 해석하였다. 익형모델은 저레이놀즈수 프로펠러 익형에 주로 이용되는 ARA-D 6%을 선택하였다. 계산된 익형의 공력 변수들과 최소에너지손실 조건을 이용하여 시위길이와 피치각 분포를 변화시킴으로써 초소형비행체의 설계조건에 적합한 가장 효율적인 프로펠러 형상을 구하였고, 현재 운용중인 Black Widow의 프로펠러 형상과 같은 설계조건에서 비교하였다. 설계결과 초소형비행체의 프로펠러에 적합하게 제공될 수 있음을 확인하였다.

• 한국신재생에너지학회:학술대회논문집
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• 한국신재생에너지학회 2010년도 춘계학술대회 초록집
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• pp.179.2-179.2
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• 2010

In this study, we have constructed the method of design about H-Darrieus wind turbine, a kind of VAWT(vertical axis wind turbine). The NACA 0012 airfoil is chosen for the blade, and DMS(double multiple streamtube) theory is used for the analysis. The flow field is computed with numerical solution of rotating Navier-Stokes equations. From the result of experimental data of power coefficient curves, the validity of the present research is checked. Through the non-dimensional parameter analysis for the wind turbine design, we estimated the efficiency of wind turbine with the resultant Cp's, with which an efficient design of VAWT is achieved, and aerodynamic characteristics are presented systematically.

• 한국신재생에너지학회:학술대회논문집
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• 한국신재생에너지학회 2005년도 제17회 워크샵 및 추계학술대회
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• pp.575-578
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• 2005

The optimum design and the performance analysis software called POSEIDON for the HAWT (Horizontal Axis Wind Turbine) was developed by use of BEMT. The Prandtl's tip loss theory was adopted to consider the blade tip loss. The lift and the drag coefficient of S-809 airfoil were predicted via X-FOIL and also the post stall characteristics of S-809 were estimated by the Viterna's equations. All the predicted aerodynamic characteristics are fairly well agreed with the wind tunnel test results, performed by Sommers in Delft university of technology. The rated power of the testing rotor is 20kW(FIL-20) at design conditions. The experimental aerodynamic parameters and the X-FOIL data were used for the power prediction of the FIL-20 respectively. The comparison results shows good agreement in power prediction.

• 신재생에너지
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• 제1권4호
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• pp.38-42
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• 2005

The optimum design and the performance analysis software called POSEIDON for the HAWT [Horizontal Axis Wind Turbine] was developed by use of BEMT. The Prandtl's tip loss theory was adopted to consider the blade tip loss. The lift and the drag coefficient of S-809 airfoil were predicted via X-FOIL and also the post stall characteristics of S-809 were estimated by the Viterna's equations. All the predicted aerodynamic characteristics are fairly well agreed with the wind tunnel test results, performed by Sommers in Delft university of technology. The rated power of the testing rotor is 20kW[FIL-20] at design conditions. The experimental aerodynamic parameters and the X-FOIL data were used for the power prediction of the FIL-20 respectively. The comparison results shows good agreement in power prediction.

• 한국전산유체공학회지
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• 제21권4호
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• pp.85-89
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• 2016

Wing is the most important part of aircraft which produces lift. In general when aircraft takes off or lands, high lift is required and additional devices are adopted in front and aft-side of wing, which constitute so-called multi element airfoils. The objective of this research is to develop a specialized grid generation program to help engineers in reducing human labor and eliminating time-consuming process for mesh regeneration by deforming the initially-given grid system with efficient deforming method. This paper describes briefly about the mesh deformation methods, and provides some results to verify the quality of deformed mesh and eventually correctness of current approach.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 1999년도 춘계 학술대회논문집
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• pp.186-191
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• 1999

An Euler solver is developed to predict accurate aerodynamic data such as lift coefficient, drag coefficient, and moment coefficient. The conservation law form of the compressible Euler equations are used in the generalized curvilinear coordinates system. The Euler solver uses a finite volume method and the second order Roe's flux difference splitting scheme with min-mod flux limiter to calculate the fluxes accurately. An implicit scheme which includes the boundary conditions is implemented to accelerate the convergence rate. The multi-block grid is integrated into the flow solver for complex geometry. The flowfields are analyzed around NACA 0012 airfoil in the cases of $M_{\infty}=0.75,\;\alpha=2.0\;and\;M_{\infty}=0.80,\;\alpha=1.25$. The numerical results are compared with other numerical results from the literature. The final goal of this research is to prepare a robust and an efficient Navier-Stokes solver eventually.

• Wind and Structures
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• 제28권3호
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• pp.191-201
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• 2019

In this paper, the aerodynamic analysis of a vertical axis wind turbine was carried out by CFD approach to optimize the turbine performance. To perform numerical simulation, SST-Transition turbulence model was used, which demonstrated more precise results compared to non-transition models. A parametric study was conducted to optimize the VAWT performance based on the selected model. The investigation of pitch angle changes showed that the highest power produced by the turbine occurs at $2^{\circ}$ angle. Considering the effect of the rotor's arm junction to the airfoil showed that by increasing the distance of the junction from the edge of the airfoil from 25 cm to 40 cm, the power of the turbine increases by 60%. However, further increase in this distance results in power decrease. Based on the proposed numerical model, a case study was conducted to consider the installation of four VAWTs in the southwest corner of the medical science building at TMU campus with a height of 42m. The results of the simulation showed that 8.27 MWh energy is obtainable annually.

• 한국전산유체공학회지
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• 제18권3호
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• pp.42-50
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• 2013

The supersonic airplane with flapped biplane, Busemann biplane equipped flap, is superior to drag and noise reduction due to wave cancelation effect between upper and lower airfoils. In this study, it is numerically calculated and analyzed the lift, drag and lift to drag ratio of flapped biplane with respect to various the length and angle of the flap. Euler solver of EDISON CFD, web based computational fluid dynamic solver for the purpose of education, is employed. Depending on the length of the flap, lift and drag increase linearly, and there exists the optimum flap angle which maximize the lift-to-drag ratio at the freestream mach 2.0 on-design condition. The predictable relational expression is driven as liner equation. As a results of comparison with drag of flapped biplane, Busemann biplane, and diamond airfoil with the same lift, the drag of flapped biplane is 88.76% lower than that of the Busemann biplane and 70.67% lower than that of the diamond airfoil. In addition, the change of pressure is compared to confirm the noise reduction effect of flapped biplane at h/c=5 of lower airfoil. The shock strength of flapped biplane is smaller than that of other airfoils.